航空发动机进口温度畸变参数和防喘控制系统设计

Research on the heat distortion parameters and the design for engine surge control systems

关键词:  航空发动机  发动机控制  防喘控制+

Key words:  Aircraft engine  Aeroengine control  Engine surge control~+

摘要:

主要研究了航空发动机防喘控制系统的设计和研制,特别是研究了当战斗机发射导弹时温度畸变对发动机的影响。引入的温度畸变参数包括:进口相对平均温升δT;进口温升率dT/dt;当量热区角Φe;连续温度畸变时间tB。通过试验和数据分析的方法得出发动机防喘控制系统的设计准则,发动机防喘控制系统的研制和飞行试验证明了该设计准则的正确性。

Abstract:

The design and development of engine surge control system,especially the parameters of heat disturbance when the fighter launches a missile,were discussed in this paper.Four heat disturbance parameters(inlet relative average temperature increment(δT);temperature rising rate(dT/dt);equivalent heat region angle(Φ_e);continuous time of heat disturbance(t_B)) were introduced and the criterion for optimal design of a engine surge control system is provided by means of tests and data analysis.A flight test with this engine surge control system has completed and it is shown that the method of design and development for engine surge control system introduced is successful.